US20110024548A1

US20110024548A1 - Launching system and launching apparatus

Info

Publication number: US20110024548A1
Application number: US12/649,808
Authority: US
Inventors: Yoshikatsu Kuroda; Yoshihiro KAWAMATA; Mika Shingo
Original assignee: Mitsubishi Heavy Industries Ltd
Current assignee: Mitsubishi Heavy Industries Ltd
Priority date: 2009-07-31
Filing date: 2009-12-30
Publication date: 2011-02-03
Also published as: EP2746156A1; JP2011033249A; EP2279945B1; RU2438940C2; EP2279945A3; EP2746156B1; CN101988813A; EP2279945A2; JP5501690B2; US8262015B2; RU2009149740A

Abstract

A flying object capable of being launched in air is detachably mounted on a wing body of a launching apparatus. The launching apparatus is towed by an aircraft through a cable so as to be run and taken off. After raising the launching apparatus to a launching height of the flying object by the aircraft, the flying object is released from the wing body in air and then the flying object is ignited and launched in air in a launching system. The system for launching in air can be developed without newly developing a platform as a mother ship so that a research cost can be remarkably reduced. In the case that a small artificial satellite is installed in a flying object, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation.

Description

TECHNICAL FIELD

The present invention relates to a launching system for launching a flying object in air and a launching apparatus therefor.

BACKGROUND ART

As a method for launching a flying object (hereinafter called as “rocket”) in air, as shown in FIG. 10, a method for releasing a rocket 2 mounted on an upper surface of an aircraft 1 from the aircraft 1, as shown in FIG. 11, a method for dropping and launching a rocket 3 attached on a lower surface of an aircraft 1 in air or as shown in FIG. 12, a method for pulling out a rocket 4 from a cargo space of an aircraft 1 with utilizing a parachute 5 and then launching the rocket 4 in air have been researched and developed.
As a rocket, a rocket having additional wings 4 detachably mounted at a rear of steering wings 3 is disclosed in a Patent Literature No. 1. Another rocket having a detachable stable wing at a moment when moving power of the rocket is down is disclosed in a Patent Literature No. 2. However, these rockets are not suitable to a method for launching a rocket in air.

CITATION LIST

{Patent Literature No. 1}

Japanese Patent Unexamined Publication No. 5-079798

{Patent Literature No. 2}

Japanese Patent Unexamined Publication No. 5-231800

SUMMARY OF INVENTION

Technical Problem

In order to develop new other methods for launching a rocket in air, it is necessary to develop an aircraft 1 as a mother ship and rockets 2, 3 and 4.
However, the methods described above have a drawback, that is, those techniques could not apply to a development of a satellite type flying object suitable for quickly observing disaster temporally happened.
The present invention is developed so as to resolve the above drawback. A purpose of the present invention is to provide a launching system and a launching apparatus wherein a rocket can be launched in air without designing a special mother ship for the rocket.

Solution to Problem

To accomplish the above purpose in a launching apparatus, a launching apparatus as recited in claim 1 is characterized in that a flying object capable of being launched in air is detachably mounted on a wing body.
To accomplish the above purpose in a launching apparatus as claimed in claim 1, a launching apparatus as recited in claim 2 is characterized in that the wing body comprises wheel member for running.
To accomplish the above purpose in a launching apparatus as claimed in claim 1, a launching apparatus as recited in claim 3 is characterized in that the wing body comprises a main wing and a vertical wing.
To accomplish the above purpose in a launching apparatus as claimed in claim 3, a launching apparatus as recited in claim 4 is characterized in that the main wing is a delta wing for generating elevation force.
To accomplish the above purpose in a launching apparatus as claimed in claim 3, a launching apparatus as recited in claim 5 is characterized in that the main wing is a joined-wing for generating elevation force.
To accomplish the above purpose in a launching apparatus as claimed in claim 1, a launching apparatus as recited in claim 6 is characterized in that the flying object comprises a head portion in which a small artificial satellite is installed.
To accomplish the above purpose in a launching apparatus as claimed in claim 1, a launching apparatus as recited in claim 7 is characterized in that the wing body has suspending means and the flying object is suspended by the suspending means, wherein the suspending means is detachable from the wing body.
To accomplish the above purpose in a launching apparatus as claimed in claim 1, a launching apparatus as recited in claim 8 is characterized in that the flying object is suspended by at least two lanyards of the wing body, wherein the at least two lanyards are detachable from the wing body, one part of the lanyards are cut so as to arrange the head portion of the flying object toward an upward direction and then the remained part of the lanyards are cut so as to release the flying object from the wing body and then the flying object is ignited and launched in air.
To accomplish the above purpose, a launching system recited in claim 9 is characterized in that the launching apparatus as claimed in claim 2 is towed by the aircraft through a cable so as to be run and taken off.
To accomplish the above purpose in a launching system as claimed in claim 9, the launching apparatus recited in claim 10 is characterized in that the launching apparatus is raised up to a launching height of the flying object by the aircraft towing the launching apparatus, and then the flying object is released from the wing body in air and then the flying object is ignited and launched in air.
To accomplish the above purpose in a launching system as claimed in claim 10, the launching system recited in claim 11 is characterized in that the small artificial satellite installed in the head portion is released after being launched the flying object in air.
To accomplish the above purpose in a launching system as claimed in claim 9, the launching system recited in claim 12 is characterized in that the wing body comprises a sensor for locking the aircraft, wherein the sensor is installed in the wing body; and a homing device for automatically controlling a control surface of the wing body so as to maintain the wing body at a proper position with respect to the aircraft in accordance with data obtained by the sensor.
To accomplish the above purpose in a launching system as claimed in claim 9, the launching system recited in claim 13 is characterized in that the wing body installs a sensor for locking the aircraft for towing and the aircraft comprises a homing device for automatically controlling the control surface so as to maintain the wing body at a proper position with respect to the aircraft in accordance with data obtained by the sensor, wherein the wing body is remote controlled by a line control method with the cable or a radio control method.
To accomplish the above purpose in a launching system as claimed in claim 9, the launching system recited in claim 14 is characterized in that the wing body released from the flying object is glided in air and retuned to the nearest airport after cutting the cable connected to the aircraft.
To accomplish the above purpose in a launching system as claimed in claim 9, the launching system as recited in claim 15 is characterized in that a winding device for winding up the cable is provided at one of the aircraft and the launching apparatus wherein an interval distance between the aircraft and the launching apparatus is adjusted by winding up/unwinding from the cable.
To accomplish the above purpose, a launching system as recited in claim 16 is characterized in that the launching apparatus as claimed in claim 1 is mounted on an upper surface or an lower surface of an aircraft and the aircraft is taken off and then the launching apparatus is released from the aircraft after raising up the launching apparatus to a launching height of the flying object by the aircraft and then the flying object is ignited and launched in air after releasing the flying object from the wing body.
To accomplish the above purpose, a launching system recited in claim 17 is characterized in that the launching apparatus as claimed in claim 1 is installed n a cargo space of an aircraft and the aircraft is taken off and then the launching apparatus is pull out from the cargo space of the aircraft after raising up the launching apparatus to a launching height of the flying object by the aircraft and then the flying object is ignited and launched in air after releasing the flying object from the wing body.

ADVANTAGEOUS EFFECTS OF INVENTION

In the launching apparatus as recited in claim 1, a rocket capable of being launched in air is detachably mounted at a wing body so that the rocket is detached from the wing body after raising the launching apparatus to a launching level of the rocket and then the rocked is ignited and launched in air.
In the launching apparatus as recited in claim 2, a wing body comprises wheels do as to run so that the wing body can be glided on a runway while the wing body is towed by the aircraft.
In the launching apparatus as recited in claim 3, a wing body has a main wing and a vertical tail assembly so that the wing body can be glided on a runway and taken off while the wing body is towed by the aircraft. Then, the wing body can be raised up to a launching height of a rocket.
In the launching apparatus as recited in claim 4, a main wing of a wing body is a delta wing for generating elevation force so that the wing body can be easily taken off while the wing body is towed by the aircraft.
In the launching apparatus as recited in claim 5, a main wing of a wing body is a joined-wing for generating elevation force so that the wing body can be easily taken off while the wing body is towed by the aircraft.
In the launching apparatus as recited in claim 6, a small artificial satellite is installed in a head portion of the rocket so that the small artificial satellite is released from the rocket after the rocket reaching to its orbit. Thus, it is possible to develop an artificial satellite smoothly and quickly applicable to security matter and disaster observation.
In the launching apparatus as recited in claim 7, a rocket is suspended from a wing body in air by a suspending member detachable from the wing body so that the rocket can be easily separated from the wing body by cutting the suspending member.
In the launching apparatus as recited in claim 8, a rocket is suspended from the wing body with two lanyards capable of being cut in air. The rocket can easily approach to its orbit for a short time immediately after launching the rocket in air since the head portion of the rocket is already arranged toward an upward direction before igniting the rocket by cutting one lanyard at first and then cutting another lanyard so as to separate the rocket from the wing body.
In the launching system as recited in claim 9, a wing body of a launching apparatus comprises wheels for running and towed by an aircraft so as to be run and taken off. By cutting the cable, the launching apparatus can be easily released from a mother ship after the launching apparatus taking off.
In the launching system as recited in claim 10, a launching apparatus towed by an aircraft is raised up to a launching level of a rocket and then the rocket is separated from a wing body in air. Then, the rocket is ignited and launched in air. Thus, it is unnecessary to develop an aircraft as a mother ship. A research cost and an operation cost can be remarkably reduced.
In the launching system as recited in claim 11, after a rocket launched in air reaching to its orbit, a small artificial satellite installed in a head portion of the rocket is released so that the satellite can be smoothly and quickly applicable to security matter and disaster observation.
In a launching system as recited in claim 12, a wing body installs a sensor for locking an aircraft for towing. The wing body comprises a homing device for automatically controlling a control surface of the wing body so as to maintain a proper position of the wing body with respect to the aircraft in accordance with data obtained by the sensor so that the wing body can be an unmanned aerial vehicle (UAV).
In a launching system as recited in claim 13, a wing body installs a sensor for locking on the aircraft for towing and a homing device for automatically controlling a control surface of the wing body so as to maintain a proper position of the wing body with respect to the aircraft in accordance with data obtained by the sensor. The wing body can be remote-controlled by a line control method with the cable or a radio control method so that a position of the wing body is automatically maintained with respect to an aircraft and the wing body can be an unmanned aerial vehicle. Further, a weight of the wing body becomes light since the wing body does not comprise a homing device therein.
In a launching system as claimed in claim 14, a wing body released from a rocket is separated from an aircraft by cutting a cable and returned to the nearest airport by flying in air so that an operation cost of the launching apparatus can be remarkably reduced.
In a launching system as recited in claim 15, an aircraft of a launching apparatus comprises a winding device for winding up a cable so that an interval distance between the aircraft and the launching apparatus can be adjusted by winging up or unwinding from the winding device. Thus, it is an advantage that a position of a wing body is maintained at a proper position by adjusting the interval distance between the launching apparatus and the aircraft.
In a launching system as recited in claim 16, a rocket capable for being launched in air is detachably attached to a wing body of a launching apparatus and the launching apparatus is mounted on an upper surface or a lower surface of an aircraft. Then, the aircraft is raised up to a launching level of the launching apparatus and then the launching apparatus is separated from the aircraft and the wing body is separated from the rocket. The rocket is ignited and launched in air, a research cost and an operation cost can be remarkably reduced except a cost for developing a suitable aircraft.
In a launching system as recited in claim 17, a rocket capable of being launched in air is detachably attached to a wing body of a launching apparatus and the launching apparatus is installed in a cargo space in an aircraft. The aircraft is raised up to a launching level of the launching apparatus and then the launching apparatus is pulled out from the aircraft and the rocket is separated from the wing body. The rocket is ignited and launched in air. Thus, a research cost and an operation cost of the launching system can be remarkably reduced except a cost developing for a suitable aircraft.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 shows a launching system of the first example according to the present invention wherein a launching apparatus is towed and glided by an aircraft.

FIG. 2 shows a top view of the launching apparatus in the launching system of the first embodiment according to the present invention.

FIG. 3 shows that a launching apparatus in the launching system of the first example according to the present invention, wherein the launching apparatus is towed by an aircraft and glided at a moment immediately before the launching apparatus taking off.

FIG. 4 shows that a launching apparatus in the launching system of the first example according to the present invention is towed by an aircraft in air.

FIG. 5 shows that a launching apparatus in the launching system of the first example according to the present invention homes an aircraft by a sensor.

FIG. 6 shows that a launching apparatus in the launching system of the first example according to the present invention suspends a rocket with a lanyard.

FIG. 7 shows that a launching apparatus in the launching system of the first example according to the present invention has two lanyards and a rocket is just suspended with one of the lanyard so as to arrange a head portion of the rocket positioned toward an upward direction.

FIG. 8 shows that a launching apparatus in the launching system of the first example according to the present invention cuts one lanyard and a rocket is ignited and launched in air.

FIGS. 9( a), 9(b) and 9(c) show a launching apparatus in a launching system of the second example according to the present invention. FIG. 9( a) shows its top view. FIG. 9( b) shows its front view. FIG. 9( c) shows it side view.

FIG. 10 shows a method for launching a rocket in air wherein the rocket is mounted on an upper surface of an aircraft.

FIG. 11 shows a method for launching a rocket in air wherein the rocket is mounted on a lower surface of an aircraft.

FIG. 12 shows a method for launching a rocket in air wherein the rocket is installed in a cargo space of an aircraft.

FIG. 13 shows a block diagram of a control system installed in a wing body in the first embodiment according to the present invention.

DESCRIPTION OF EMBODIMENTS

Concerning with the best mode to do the present invention, it will be described with reference to the following description.

Example 1

- A launching system of the first example according to the present invention is shown in FIG. 1 to FIG. 8.

The launching system of the example as shown in FIG. 1 to FIG. 8 comprises a launching apparatus 10 towed by an aircraft 30 through a cable 20 so as to take off the launching apparatus 10 from a runway 100 in a method for towing the launching apparatus 10, wherein a rocket 11 is detached from a wing body 12 of the launching apparatus 10 and the rocket 11 can be launched in air.
For instance, a rocket is enough small and the rocket can install a small artificial satellite in its head portion and the small artificial satellite can be released from the small rocket and put the small artificial satellite on a low-degree orbit, that is, a height of 300 km through 800 km from the earth. It is unnecessary for the rocket 11 to provide anyone except a wing body 12.
As shown in FIG. 1 and FIG. 2, the wing body 12 comprises wheel members 12 a and 12 b wherein the wheel members 12 a and 12 b is provided at a front portion and a rear portion of the wing body 12, respectively so as to be glided on the runway 100. The wing body 12 comprises a vertical tail assembly 12 c at a rear portion of the wing body 12. Further, as shown in FIG. 2, a delta wing 12 d is provided as a main wing so as to generate elevation force. The delta wing 12 d is a flat-shaped wing. A front edge of the delta wing has a swept-back angle and a rear edge of the delta wing is arranged perpendicular to a longitudinal axis of the aircraft. In a view of a point above the delta wing, the delta wing 12 d is looks like a triangle shape. The delta wing 12 d generates elevation force and the launching apparatus 10 is towed by the aircraft 30 so that the launching apparatus 10 can be easily taken off.
Although the wing body 12 does not employ any driving device for taking off by itself, the wing body 12 may install an auxiliary driving device so as to assist its flight when the wing body 12 is glided.
The wing body 12 is an “Unmanned Aerial Vehicle (UAV)” and comprises a control system as shown in FIG. 13 so as to home the aircraft 30 towed by the wing body 12.
In the wing body 12 as shown in FIG. 13, there are a sensor 40 for homing the aircraft 30 towed by the wing body 12 and a homing device 50 for controlling a control surface of the aircraft 20 so as to maintain a position of the wing body 12 in a constant style with respect to the aircraft 30.
As shown in a dot-line in FIG. 5, the sensor 40 locks the aircraft 30 while the launching apparatus is towed by the aircraft 30 in air.
The homing device 50 controls the control surface of the wing body 12 by adjusting a part of a wing body (flap) in order to maintain the aircraft 30 locked by the sensor 40 at a constant style with respect to the wind body 12. In practically, as shown in FIG. 13, an actuator 60 controls the flap 70 of the vertical tail wing 12 c or the delta wing 12 d.
Alternatively, the homing device 50 may not be installed in a wing body and may be installed in an aircraft 30 by utilizing a line control method with a cable or a radio control method so as to control the control surface of the wing body 12 from a remote location. In the above case, a redundant device such as a homing device 50 is unnecessary in the wing body 12 and the position of the wing body 12 can be stably maintained at a constant style with respect to the aircraft 30.
Further, a winding device (not shown) for winding a cable 20 may be provided at an aircraft or a launching apparatus 12. The winding device winds up the cable 20 and unwinding the cable 20 up, so that an interval distance between the aircraft 30 and the launching apparatus 10 can be adjusted. By utilizing the adjustment, the length between the aircraft 30 and the launching apparatus 10 becomes suitable so that a position of the wing body 12 can be set in a preferable style with respect to the aircraft 30.
Although the wing body 12 as shown in FIG. 1 through FIG. 8 is drawn exaggeratedly, that is, the wing body 12 is drawn larger than a real one, the wing body 12 is actually much smaller than the aircraft 30. For instance, a total length of the wing body is about 10 m and a total width thereof is about 8 m.
If an aircraft 30 tows the launching apparatus 10 and then the launching apparatus 10 is taken off, it is unnecessary to develop a special aircraft.
For example, it is possible to utilize a passenger plane, a cargo plane, a transport plane and so on.
By utilizing the launching system of the first example described above, the launching apparatus 10 is towed by the aircraft 30 with the cable 20 and taken off. When the launching apparatus 10 is raised to a launching level, the rocket 11 is released from the wind body 12 and then the rocket 11 can be ignited in air.
That is, as shown in FIG. 3, the launching apparatus 10 is towed by the aircraft 30 with the cable 20 and run on a runway 100 so as to be taken off. Then, the rocket 11 can be raised to a launching level. As shown a dot-line in FIG. 5, the wing body 12 homes the aircraft 30 for towing the wing body 12 by the sensor 40. In accordance with data obtained by the sensor, the surface control of the wing body 12 can be automatically adjusted with respect to the aircraft.
As shown in FIG. 6, a rocket 11 is suspended by the wing body 12 with two lanyard 13 a and 13 b, wherein the lanyards can be cut off and one lanyard 13 a is arranged at a front portion and another lanyard 13 b is arranged at a rear portion of the wing body 12. The lanyards 13 a and 13 b are merely one of examples for suspending the rocket 11. It is also possible to utilize a wire, a chain or a suspending rope and so on. A number of lanyards is not restricted two, if the number is plural.
As shown in FIG. 7, the rear lanyard 13 b is cut off and the rocket is suspended with the front lanyard 13 a. A head portion of the rocket 11 is arranged in an upward direction. And then, as shown in FIG. 8, by cutting off the front lanyard 13 a, the rocket 11 is separated from the wing body 12 and the rocket 11 is ignited in air so as to be launched toward a front-inclined direction.
In the present example, the rocket 11 is suspended by the two lanyards 13 a and 13 b. The rocket 11 can be easily separated from the wing body 12 by cutting off the front lanyard 13 a and the rear lanyard 13 b.
The rocket 11 is launched in air while the head portion of the rocket 11 is arranged toward a upward direction. It is a merit that the rocket 11 can be raised up immediately after launching and the rocket 11 can reach to its orbit for a short time.
In the above example, the rocket 11 is suspended by two lanyards 13 a and 13 b. However, if a number of lanyards are the plural, any plural number is acceptable. In the case, the head portion of the rocket is arranged toward a front direction. The front lanyard may be cut off after the rear lanyard is cut off at first so as to launch the rocket toward a front inclined direction. Of course, the other arrangement is acceptable.
For instance, in the case that a head portion of a rocket 11 is arranged toward a rear direction, the rear lanyard 13 b is cut off after the front lanyard 13 a is cut off at first so as to launch the rocket 11 toward rear inclined direction.
In the case, the rocket is launched in air toward a direction opposite to a flying direction of the aircraft 30. Thus, the rocket can be launched more safety.
It is the easiest way that a cable 20 connecting with a wing body 12 from which the rocket 11 has been already separated and the aircraft 30 is cut and the wing body 12 is wasted after launching the rocket in air. However, if the wing body 12 from which the rocket 11 has been already separated is still towed by the aircraft 30 and landed on the nearest airport, an operation cost concerning about a launching apparatus can be remarkably reduced.
If a cable 20 connecting between an aircraft 30 and a wing body 12 is cut and the wing body 12 can glide in air and be navigated so as to land on the nearest airport, an operation cost concerning about a launching apparatus can be remarkably reduced as similar as above.
Further, although the wing body 12 and the aircraft 30 are connected with the cable 20 as shown in FIG. 8 at a moment when the rocket 11 is ignited in air, the other cases are acceptable in the present invention. For instance, before the rocket 11 ignited and launched in air, the cable connected between the wing body 12 and the aircraft 20 may be cut and the aircraft 30 is escaped to a safety air zone, the launching operation becomes more safety.
As descried above, in accordance with the launching system of the present example, the launching apparatus 10 is towed and taken off by the aircraft 30 with a cable. The launching apparatus 10 is raised to a launch level and then the rocket 11 is ignited and launched in air by releasing the rocket 11 from the wing body 12. Thus, the wing body 12 of the present example is unnecessary a special mother ship. Thereby, a launching system for launching a rocket in air can be developed with a remarkably low cost. On the other hand, it is unnecessary to develop an aircraft 30 as a mother ship so that a development cost and an operation cost can be remarkably reduced.
Particularly, if a rocket 11 installs a small artificial satellite at a head portion, the small artificial satellite can be discharged after the rocket 11 is reached on an orbit. Thereby, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation.

Example 2

FIG. 9 shows the second example according to the present invention. The second example utilizes a joined-wing 80 for generating elevation force instead of a delta wing 12 d as a main wing of the wing body 12 of the first example.
As shown in FIG. 9, the joined-wing 80 has a structure that a vertical tail assembly with a sweptforward angle is joined to a main wing 81 with a sweptback angle. The joined-wing 80 can generate elevation force equal or larger than that generated by the delta wing 12 d of the first example.
In the second example, a rocket 11 can be separated from a wing body 12 with the joined-wing 80 as a main wing so that the effect and the advantage of the second example are as same as those of the first example.

Example 3

The examples 1 and 2 as described above employ a tow method for towing a launching apparatus 10 by an aircraft 30. The third example does not employ the tow method and employs an improve method by improving a conventional air launching method as described in the Background Art. The third example can be largely divided into two methods.
A method is as follows:

(1) A launching apparatus is taken off with an aircraft wherein the launching apparatus is mounted on an upper surface or a lower surface of the aircraft. As described in the first example, a rocket capable for launching in air is detachably attached to a wing body.
(2) The launching system is raised to a launching level by the aircraft.
(3) As similar as the first example, the rocket is separated from the wing body and then the rocked is ignited and launched in air.

The other method is as follows:

(1) An aircraft is taken off wherein a launching apparatus is installed in a cargo space of the aircraft. As described in the first example, a rocket capable for igniting in air is detachably attached to a wing body.
(2) The launching system is raised to a launching level for launching the rocket by the aircraft.
(3) The launching system is pull out from the cargo space of the aircraft.
(4) After that, as similar as the first example as described above, the rocket is released from the wing body and the rocket is ignited and launched in air.

According to the third example, a launching apparatus is not towed by an aircraft. A rocket is mounted on an aircraft or installed in a cargo space of an aircraft and then the aircraft is taken off. Upon comparing with the tow method in the first and second examples and the present method of the third example, there is an advantage that a necessary length of a runway on which the aircraft is taken off is shorter than that of the first and second examples.
Particularly, if an aircraft has been already developed, a present method for launching a rocket in air can be launched with a remarkably low cost.

INDUSTRIAL APPLICABILITY

In the present invention, a cost for developing a system for launching a rocket in air can be remarkably reduced. Particularly, a rocket in which a small artificial satellite is installed can be launched systematically with a low cost. It is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation and so on. Therefore, the present invention can be utilized in various industrial fields.

REFERENCE SIGNS LIST

10 . . . launching apparatus
11 . . . rocket
12 . . . wing body
12 a, 12 b . . . wheel
12 c . . . tail assembly
12 d . . . delta wing
13 a, 13 b . . . lanyard
20 . . . cable
30 . . . aircraft
40 . . . sensor
50 . . . homing apparatus
60 . . . actuator
70 . . . flap
80 . . . joined-wing

Claims

1. A launching apparatus characterized in that a flying object capable of being launched in air is detachably mounted on a wing body.

2. A launching apparatus as claimed in claim 1 characterized in that said wing body comprises wheel member for running.

3. A launching apparatus as claimed in claim 1 characterized in that said wing body comprises a main wing and a vertical wing.

4. A launching apparatus as claimed in claim 3 characterized in that said main wing is a delta wing for generating elevation force.

5. A launching apparatus as claimed in claim 3 characterized in that the main wing is a joined-wing for generating elevation force.

6. A launching apparatus as claimed in claim 1 characterized in that said flying object comprises a head portion in which a small artificial satellite is installed.

7. A launching apparatus as claimed in claim 1 characterized in that said wing body has suspending means and said flying object is suspended by said suspending means, wherein said suspending means is detachable from said wing body.

8. A launching apparatus as claimed in claim 1 characterized in that said flying object is suspended by at least two lanyards of said wing body, wherein said at least two lanyards are detachable from said wing body, one part of said lanyards are cut so as to arrange said head portion of said flying object toward an upward direction and then the remained part of said lanyards are cut so as to release said flying object from said wing body and then said flying object is ignited and launched in air.

9. A launching system characterized in that said launching apparatus as claimed in claim 2 is towed by said aircraft through a cable so as to be run and taken off.

10. In a launching system as claimed in claim 9, said launching system characterized in that said launching apparatus is raised up to a launching height of said flying object by said aircraft towing said launching apparatus, and then said flying object is released from said wing body in air and then said flying object is ignited and launched in air.

11. In a launching system as claimed in claim 10, said launching system characterized in that said small artificial satellite installed in said head portion is released after being launched said flying object in air.

12. In a launching system as claimed in claim 9, said launching system is characterized in that said wing body comprises a sensor for locking said aircraft, wherein said sensor is installed in said wing body; and a homing device for automatically controlling a control surface of said wing body so as to maintain said wing body at a proper position with respect to said aircraft in accordance with data obtained by said sensor.

13. In a launching system as claimed in claim 9, said launching system characterized in that said wing body installs a sensor for locking said aircraft for towing and said aircraft comprises a homing device for automatically controlling said control surface so as to maintain said wing body at a proper position with respect to said aircraft in accordance with data obtained by said sensor, wherein said wing body is remote controlled by a line control method with the cable or a radio control method.

14. In a launching system as claimed in claim 9, said launching system characterized in that said wing body released from said flying object is glided in air and retuned to the nearest airport after cutting the cable connected to said aircraft.

15. In a launching system as claimed in claim 9, said launching system characterized in that a winding device for winding up said cable is provided at one of said aircraft and said launching apparatus wherein an interval distance between said aircraft and said launching apparatus is adjusted by winding up/unwinding from said cable.

16. A launching system characterized in that said launching apparatus as claimed in claim 1 is mounted on an upper surface or an lower surface of an aircraft and said aircraft is taken off and then said launching apparatus is released from said aircraft after raising up said launching apparatus to, a launching height of said flying object by said aircraft and then said flying object is ignited and launched in air after releasing said flying object from said wing body.

17. A launching system characterized in that said launching apparatus as claimed in claim 1 is installed n a cargo space of an aircraft and said aircraft is taken off and then said launching apparatus is pull out from said cargo space of said aircraft after raising up said launching apparatus to a launching height of said flying object by said aircraft and then said flying object is ignited and launched in air after releasing said flying object from said wing body.